Dirigible aeroplane



J. FOX

DIRIGIBLE AEROPLANE May 31, 1927. D 1,630,336

Filed March 26, 1926 2 Sheets-Sheet 1 IN VEN TOR JZZLZLS EX ATTORNEY1,630,336 May 31, 1927. FOX

DIRIGIBLE AEROPLANE Filed March 26, 1926 2 Sheecs-Sheev 2 IN VEN TORLilacs Fbx A TTORNE Y Patented May 31, 1927.

JULIUS FOX, F CLEVELAND, OHIO, ASSIGNOR OF ONE-FOURTH T0 JOSEPH H. GRUM-MER AND ENE-FOURTH 'IO EUGENE 0. LA FEVRE, BOTH 0F CLEVELAND, OHIO.

DIBIGIIBLE AEROPLANE.

Application filed March 26, 1926. Serial No. 97,492.

This invention relates generally to aeroplanes, the invention havingmore particular reference to a novel type of dirigible aeroplane.

The invention has for an object the provision of a dirigible aeroplane,which will prevent accidents due to stalled motors and the like whileflying, as the helium used in connection with my improved device Wlll 36enable my improved dirigible aeroplane to float in the air.

Another ob'ect of the invention is the provision of a irigible aeroplanehaving increased flying area, as the helium used in 35 connection withmy improved device will enable the motor to be stopped, when prevailingwinds are favorable.

A further object of the invention is the provision of a dirigibleaeroplane having a means of gassing or exhausting the helium used inconnection with my improved device, as may be required to raise or lowerthe dirigible aeroplane, when the ordinary means for this purpose isdisabled, so as to allow continued use of my dirigible aeroplane, and

prevent accidents.

For further comprehension of the invention, and of the objects andadvantages thereof, reference will be had to the following descriptionand accompanying drawings, and to the appended claims inwhich thevarious novel features of the invention are more particularly set forth.

Fig. 1 of the drawings, is a front elevational view of my improveddirigible aeroplane.

Fig. 2 of the drawings, is a top plan View thereof.

Fi 3 of the drawings, is an enlarged perspectlve view of the wing,thereof, showing the helium tanks.

Fig. 4 of the drawings, is a side elevational view, showingamodification of my improved dirigible aeroplane.

Fig. 5 of the drawings, is a top plan view thereof.

Fig. 6 of. the drawings, is an enlarged perspective view of the wingthereof, showing the helium tanks.

5 Referring in particular to Figs. 1 and 2 of the accompanying drawings,the underbody 10, the wheels 11, the wings 12, propeller 13. the motor14, and the adjustable wing members 15, are of common ordinaryconstruction such as generally embodied in aeroplanes of this type.

The tanks 16, may be of any suitable size 7 and shape, preferably suchas will fill the space, adjacent to and between the-upper longitudinalstruts 17 and the lower longitudinal struts 18, the forward verticalbraces 19 and the rear vertical braces 20, of the wings 12. The heliumtanks 16 are rovided with suitable connections 21, exten ing preferablydownward therefrom, and having valves 22 with convenient hand wheels 23,or any similar suitable handles for closing and opening the said valves22, so as to allow helium to be taken into, or exhausted from the saidtanks 16.

It being understood that I do not necessarily limit the above mentionedconstruction to the aeroplane as above described.

Referring in particular to Figs. 4 and 5, of the accompanying drawing,in which I have illustrated a modification of my improved dirigibleaeroplane, the motors 24, the propellers 25, the forward wings 26, therear wings 27, and the heretobefore mentioned component parts, as hereshown and designated by similar reference numerals,

are of common ordinary construction such as generally embodied inaeroplanes of'this type.

The tanks 28, may be of any suitable size and shape, preferably such aswill fill the space, adjacent to and between the upper longitudinalstruts 29, the lower longitudinal struts 30, and the forward verticalbraces 31, and the rear vertical braces 32, of the forward wings 26. Thetanks 33, may be of any suitable size and shape, preferably such as willfill the space adjacent to and between the upper longitudinal struts 34,the lower longitudinal struts 35, and the forward vertical braces 36,and the rear vertical braces 37 of the rear wings 27.

The tanks 28 and 33, are provided with connections 38, having suitablevalves 39 with pinions 40 operatively attached thereto, and meshing withsuitable gears 41, rigidly attached to the shafts 42, which arerotatively mounted in suitable bearings car-- ried in the supports 43,rigidly attached to the hereinbefore mentioned win as at 44. The shaft42 has rigidly attac ed thereto bevel pinions 45, meshing with the bevelgears 46, rigidly attached to the second shafts 47, rotatively mountedin suitable bearings-48, attached to any convenient part of heretoforementioned dirigible aeroplane, so that the hand wheels 49, rigidlyattached to the second shafts 47, are within reach of the operator of myimproved device, so as to permit the operator to open the valves 38, andrelease or exhaust any part or all of the helium contained therein.

It will be further understood that the above mentioned construction is apreferred embodiment of my invention. It is to be understood that I donot limit myself to the precise construction herein disclosed, and theright is reserved to all changes and modifications comlng within thescope of the invention as defined in the appended claims.

. Having thus described my invention, what I claim as new and desire toprotect by Letfers Patent of the United States is as folows:

1. In a device of the class described, a dirigible aeroplane comprisingfront and rear wings, struts comprising spaced members supporting saidwing, means for retaining as 'of a weight lighter than air mountedetween the spaced members of the struts of saidv front and rear wings,valve mechanism for controlling the gas content of said retaining meanswhile said aeroplane is in operation to selectively vary the liftingpower of the front and rearwings of said aeroplane for effecting changesin the direction .of movement thereof.

2. In a device of the class described, a dirigible aeroplane comprisingfront wing, meansfor retaining gas of a weight lighter than air mountedon the front wings of said aeroplane, valve mechanism for controllingthe gas content of said-retaining means for varying the lifting power ofsaid front wings while said aeroplane is in operation, rear wings, meansfor retaining gas of a weight lighter than air mounted on said rearwings, valve mechanism for varying the content of gas in said rearwings, and operating mechanism for said valve mechanism convenientlylocated in the pilot house'of said aeroplane for selectively varying thegas content of said front and rear retaining means for changing theelevation of the front of said aeroplane relative to the rear thereof.

In testimony whereof I have afiixed my signature.

JULIUS FOX.

